Rotating jet motor with regulation of power output



March 1954 J. VILLEMEJANE 2,67 5

ROTATING JET MOTOR WITH REGULATION POWER OUTPUT Filed Oct; 9, 1947 3 Sheets-Sheet 1 Fig].

Filed Oct. 9. 1947 March 2, 1954 E 2,670,597

ROTATING JET MOTOR WITH REGULATION POWER OUTPUT 3 Sheets-Sheet 2 Y j1s Z .22 ventaz March l954 JfVlLLEMEJANE 7 2,670,597

ROTATING JET MOTOR WITH REGULATION POWER OUTPUT 4 Fild Oct. 9, 1947 5 sheets-sheet s Patented Mar. 2, 1954 ROTATING: JET. MQ DOR WITH REGULATIQN. OF POWER OUTPUT Jacques Vill'emjane; Paris, France- Application October 9, L947, Serial No. 778,781

Claims priority; application France October 14, I946- 6. Claims. (01. GDP-39.2)

This invention relates to: heat engines. of: the.

type incorporatinga; series of: Venturi-shapeiii chambers wherein combustion: gases operate. and

are ejected by means or a final nozzle either into the outer atmosphere or into thebl'ades 01" a turbine or reactor soas to produce motive force- The main object of my invention consists. in increasin the mass of combustion gasesin eachsuccessive chamber, and consequently their velocity. With this object in view, the device according to my invention comprises a succession of Venturi-shaped combustion chambers, each hav-. ing an inlet of atmospheric air and a burner sup.- plied with fuel, an ejection nozzle being located at the outlet of the final combustion chamber, which nozzle ejects the gases into the surround.- ing' atmosphere or into aturbine or reactor.

In order to stillfurther increase the mass of. combustion gases, a portion of the gases passing out ofthe ejection nozzle is recycled into one.

of the combustion chambers, preferably the first of'said chambers.

In the'accompanying drawings-which show diagrammatically and byway of example, several embodiments of my invention:

Fig. l is an axial section ofa plurality: of

Venturi-shaped combustion chambers arranged in series to form part of a heat engine.

Fig. 2 is an axial section illustrating a similar series of chambers, one of which is provided with central mixing means.

Figure-3 is an axial sectionthrough-lineIlI-JII of Figure 4, of a turbine having aplurality of series of chambers'of the type illustrated in Fig; 1, said series being arranged radially.

Fig. 4 is a cross-section through line IV-JV of Figure 3.

Fig. 5 is an axial section through line of Fig. 6, of a turbine having a single series of axially arranged chambers according to Fig. 1,

and Figure 6 is a cross section through line VI-VI of Figure 5.

Figure 7 is an axial section, through line VII-- VII of Figure 8, of an engine provided with: combustion. chambers tangentially arranged with re erence to a rotary disc, and Fig.8 is a cross section; through line VIIIVIII of Fig. 7..

Fig. 9- is. an axial section through line. IX-JX of Fig. 10, of an engine the tangentially arranged combustion chambers of which open into a turbine blading, and

Fig: 10; is a part sectional view through; line.

X-X of Fig; 9.

Turning, to Fig. l, the first. combustion. chamher it of a series. of chambers forming part of the heat engine. is. provided with. an air inlet 6 and. the. following combustion chambers l0, l5, l5: arelikewise provided with air; inlets 11,, 1,. H. Each combustion chamber has, a, double walled jacket 2, 3 within which fuel is fed by a common duct: 8 to supply burners: 5 5= inside each cham ber. An. ejection nozzle e is placed at the outlet of the final combustion chamber IS.

The fuel burning in each burner 5 sucks in atmospheric air through the corresponding inlet 5, M, H- The jacket walls 2, t ct the combos tion chambers. h, til, l5, l5. are cooled by the; fresh incoming fuel; and the heat produced the combustion gases in each. chamber causes vaporisation. of the fuel thus supplied to. the burners through. the duct 8. The burnt gases; from all the chambers are exhausted through-the nozzle e.. The gases issuing. from the nozzle 6 will provide the propulsion of a vehicle-through reaction or they. may operate a turbine as di'se closed hereinafter. On starting, when. still cold',.. the engine may be heated by any known means. not illustrated.

The velocity of the gases increases eaclr time they pass through the outlet ot any 'of the combustion chambers h, It and I5; If M be the mass of gases and V their velocity at the-outlet end of chamber h, the mass of gases in chamber ill; will: be. increased: by: that or theair entering at H and will amount to 2M, for instance, at the outlet of chamber I0, and. their velocity will be 2V. Through the arrangement of a third Venturi tube l5 after chamber Ill, the-mass will become 4M and. the velocity. 4V, and so forth.

In order to still further increase the mass andvelocity of the gases, a portion of the gases may Ice-recycled from the outlet end of the final combustionchamber I5 and for this purpose, a pipe, it will feed said portion of gases back into. the first: combustion chamber 71. or into any of the other chambers It, [5, l5.

In Fig. 2, the Venturi chamber or tube 10. which forms thesecond combustion. chamber is provided with a central core l2= forcing the. flame outwardly to commingle with the. air entering at l I. Said core I2 may be hollow. In such a case, the fuel supplied: by. the pipev 81 to the jacket between the walls,- 2; 3-. of chamber l0. and heated. therein is fed through. the channels l3, I3 to the chamber inside the core l2: and thence throughthe pipe. 1.4 to the jacket between the Walls 2, 3' of the. preceding chamber h. The heat absorbed by the. gases cooling the core. l2 produces in-I creased pressure and velocity for: the. gases flow.- ingoutof the core.

The successive Venturi chambers h, H11 and; 1 .5; 15. which constitute thermal accelerators may be disposed along radial lines, as in FiguresB and 4, from thecenter tothe periphery of a plate keyed to the engine shaft. The gases are caused to impinge. on the-blades of a turbinei rotating in A to the suction exerted by the successive Venturi chambers to suck air out of the latter into the turbine.

In the case illustrated in Figs. and 6, a single series of combustion chambers is laid along the axi of the engine. A portion of the gases may be recycled through the pipe it from the peripheral exhaust nozzle 2 into the inlet of the first chamber h, and the remainder will be sent into the turbine i! for driving same.

As shown in Figs. 7 and 8 one or more series of Venturi tubes or chambers may be arranged on the plate 18, at the periphery thereof in a direction tangential to the direction of rotation. A shunt pipe I6 from the final outlet nozzle for the burnt gases returns a portion of the latter back to the inlet of the first combustion chamber as in the case illustrated in Fig. 1.

In Figs. 9 and 10, several series of Venturishaped combustion chambers are disposed in succession tangentially to the periphery of a plate (2 and they project the burnt gases against the blades 2' of a turbine which rotate in a direction opposed to that of the plate at. In order to vary the angle of impact of the gases on the blades of the turbine rotor z, each or" the final nozzles e may be pivotally secured to a spindle 20 and angularly adjusted thereon through a rod [9 operable by a lever 21 mounted on the motor shaft and to which a, slight rotation may be imparted round the axis of said shaft by a bar 2&3 provided with a knob 24 and threadedly carrying a nut 23 adapted to lock the bar 25 in any desired position.

What I claim is:

l. A thermal motor comprising a motor shaft, arotor mounted on said shaft, a plurality of series, of Venturi-shaped combustion chambers carried by said rotor with their respective axes tangential to a circle having its center on the axis of said shaft, said chambers opening directly into one another, each combustion chamber being arranged to feed the next chamber with burnt gases, a burner in each chamber, a supply of fuel to each burner, an air inlet to each chamber, a nozzle at the outlet end of the final combustion chamber of each series, the respective discharge ends of said nozzles being located on a circle coaxial with the first mentioned circle and of greater diameter so that the stream of burnt gases issuing from each of said nozzles is discharged on the outside of the first air inlet of the next series of combustion chambers, and a shunt passage connecting each of said nozzles with the first air inlet of the next series of com bustion chambers.

2. A thermal motor comprising a motor shaft, a rotor mounted on said shaft a plurality of series of Venturi-shaped combustion chambers with their respective axes tangential to a circle having its center on the axis of said shaft and located in a plane at right angles to said axis, said chambers opening directly into one another whereby each combustion chamber feeds burnt gases to the next chamber, a burner in each chamber, a supply of fuel to each burner, an air inlet to each chamber, a nozzle at the outlet end of the final combustion chamber of each series, the respective discharge ends of said nozzles being located on a circle coaxial with the first mentioned circle and of greater diameter so that the stream of burnt gases issuing from each of said nozzles is discharged on the outside of the first air inlet of the next series of combustion chambers, and a shunt conduit extending from an intermediate point of each of said nozzles to the air inlet of the first combustion chamber of the next series.

3. In a heat engine, a rotor shaft, a rotor mounted on said shaft, a plurality of series of combustion chambers carried by said rotor, said chambers opening axially into one another to feed one another with the burnt gases evolved therein, a nozzle at the output end of the last chamber of each series adapted to produce a high velocity stream of burnt gases, a jacket surrounding each chamber, means for feeding fuel to the different chamber jackets, burners in each combustion chamber fed with fuel through the corresponding jacket, means for admitting atmospheric air into the inlet end of each chamber, and a turbine rotor j ournalled concentrically on said rotor on the outside of said series of combustion chambers and including blades adapted to be submitted to the stream of burnt gases passing out of the nozzles of the different series.

4. In a heat engine, a rotor shaft, a rotor mounted on said shaft, a plurality of series of combustion chambers carried by said rotor. said chambers opening axially into one another to feed one another with the burnt gases evolved therein, a nozzle at the output end oi the last chamber of each series adapted to produce a high velocity stream of burnt gases, a jacket surrounding each chamber, means for feeding fuel to the difierent chamber jackets, burners in each combustion chamber fed with fuel through the corresponding jacket, means for admitting atmospheric air into the inlet of each chamber, a turbine rotor journalled concentrically on said first mentioned rotor on the outside of said series of combustion chambers and including blades adapted to be submitted to the streams of burnt gases passing out of the nozzles of the different series, and means for adjusting the angle of the axes of said nozzles with reference to the radii of the first mentioned rotor passing through said nozzles.

5. A motor according to claim 1 in which said series of combustion chambers are mounted on a rotating disc.

6. A thermal motor according to claim 2 further including a turbine rotor journalled on said shaft concentrically on said first mentioned rotor on the outside of said series of combustion chambers-and including blades arranged to be submitted to the stream of burnt gases passing out from said nozzles. H

JACQUES VILLEMEJANE.

References Cited in the file of this patent UNITED STATES PATENTS Number Name Date Re. 22,844 Traupel Feb. 18, 1947 1,003,708 Coleman Sept. 19, 1911 1,146,707 Holtz July 13, 1915 1,291,273 Tyler Jan. 14, 1919 1,802,860 Zwinkel Apr. 28, 1931 1,987,699 Moore Jan. 15, 1935 FOREIGN PATENTS Number Country Date 522,163 France Mar. 22, 1921 627,121 France May 30, 1927 804,213 France July 27, 1936 807,419 France Oct. 19, 1936 90,784 Germany Feb. 15, 1897 299,420 Great Britain May 15, 1930 263,415 Italy Mar. 16, 1929 

